Select the correct statement for a Mach wave.(a) M > 1(b) \(\frac {P_2}{P_1}\)=0.528(c) \(\frac {T_2}{T_1}\)=1(d) \(\frac {\rho_2}{\rho_1}\)=∞I got this question in quiz.Origin of the question is Flow Compressible topic in portion Normal Shock Waves of Aerodynamics

Select the correct statement for a Mach wave.(a) M > 1(b) \(\frac {P_2

1.	Select the correct statement for a Mach wave.(a) M > 1(b) \(\frac {P_2}{P_1}\)=0.528(c) \(\frac {T_2}{T_1}\)=1(d) \(\frac {\rho_2}{\rho_1}\)=∞I got this question in quiz.Origin of the question is Flow Compressible topic in portion Normal Shock Waves of Aerodynamics
Answer» Correct choice is (c) \(\frac {T_2}{T_1}\)=1 For explanation: A Mach wave is a NORMAL shock wave of diminishing strength. It occurs for M=1 upstream. Then downstream M=1 ALSO. And all the ratios are equal to 1, i.e \(\frac {P_2}{P_1}\)=1, \(\frac {T_2}{T_1}\)=1, \(\frac {\rho_2}{\rho_1}\)=1. This can be found by CALCULATION when we put m=1. The properties across Mach wave do not change.

Discussion

No Comment Found

Related InterviewSolutions

The total temperature across the normal shock wave is constant. Which statement gives the wrong reason for this?(a) Adiabatic flow across normal shock wave(b) Normal shock wave has an isentropic flow(c) Calorifically perfect gas(d) Thermal dissipation thereI got this question in quiz.I want to ask this question from Flow Compressible topic in chapter Normal Shock Waves of Aerodynamics
Mach number is a measure of the directed motion of the gas compared with the random thermal motion of the molecules.(a) False(b) TrueThis question was posed to me during an interview for a job.The origin of the question is The Basic Normal Shock Equations in chapter Normal Shock Waves of Aerodynamics
The fundamental expression for the speed of sound in a gas is not given by which of the following equations?(a) a^2=\(\frac {dp}{d\rho }\)(b) a=\(\sqrt {(\frac {\partial p}{\partial \rho })s}\)(c) a=\(\sqrt {\frac {\gamma p}{\rho }}\)(d) a=\(\sqrt {\gamma ^2RT}\)I had been asked this question in examination.This intriguing question comes from The Basic Normal Shock Equations topic in section Normal Shock Waves of Aerodynamics
A shock wave that is normal to the upstream flow is a rare case.(a) False(b) TrueI have been asked this question in a national level competition.I need to ask this question from The Basic Normal Shock Equations in division Normal Shock Waves of Aerodynamics
Select the incorrect statement out of the following.(a) limτs→0⁡ is the case of an incompressible flow(b) Speed of sound in incompressible medium is zero(c) Mach number for finite velocity object, in incompressible flow is zero(d) Incompressible flow is theoretically zero-Mach number flowsThe question was asked in exam.The query is from The Basic Normal Shock Equations topic in division Normal Shock Waves of Aerodynamics
For subsonic compressible flow, which of these is not required to be measured separately to find the velocity of flow?(a) Stagnation pressure(b) Static pressure(c) Mach number(d) Free-stream of soundThe question was posed to me in an interview.This key question is from Measurement of Velocity in a Compressible Flow topic in portion Normal Shock Waves of Aerodynamics
For a non-perfect gas, if we double the pressure while keeping the temperature same, the speed of sound remains the same.(a) False(b) TrueI got this question in exam.I want to ask this question from The Basic Normal Shock Equations in section Normal Shock Waves of Aerodynamics
A normal shock wave can be specified with a single velocity.(a) True(b) FalseThe question was posed to me in an online interview.Asked question is from Flow Compressible in portion Normal Shock Waves of Aerodynamics
Select the false statement for the normal shock wave.(a) Entropy increases across normal shock wave(b) Normal shock wave has velocity and pressure gradients(c) Shock wave is pretty thick(d) Thermal and frictional dissipation thereI had been asked this question in an interview for internship.Question is taken from Flow Compressible in portion Normal Shock Waves of Aerodynamics
Which of the following is incorrect for a normal shock wave?(a) M1=1 then M2=1(b) M1 > then M2 > 1(c) M\(_1^*\)=1→M\(_2^*\)=1(d) M1→∞ then M2=finite valueI had been asked this question in homework.Asked question is from Flow Compressible in chapter Normal Shock Waves of Aerodynamics

Select the correct statement for a Mach wave.(a) M > 1(b) \(\frac {P_2}{P_1}\)=0.528(c) \(\frac {T_2}{T_1}\)=1(d) \(\frac {\rho_2}{\rho_1}\)=∞I got this question in quiz.Origin of the question is Flow Compressible topic in portion Normal Shock Waves of Aerodynamics

Discussion

No Comment Found

Related InterviewSolutions

Reply to Comment